Airworthiness Directives; Airbus Airplanes, 16248-16251 [2018-06591]
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16248
Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0169; Product
Identifier 2017–NM–095–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2015–02–
17, which applies to all Airbus Model
A330–200, A330–200 Freighter, and
A330–300 series airplanes. AD 2015–
02–17 requires revising the electrical
emergency configuration procedure in
the Emergency Procedures section of the
airplane flight manual (AFM) to include
procedures for deploying the ram air
turbine manually to provide sufficient
hydraulic power and avoid constant
speed motor/generator (CSM/G)
shedding. Since we issued AD 2015–02–
17, we have determined that
replacement or modification of the two
flight warning computers (FWCs) is
necessary to address the identified
unsafe condition. This proposed AD
would add a requirement to replace or
modify the two FWCs. This proposed
AD would also remove airplanes from
the applicability. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by May 31, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone: +33 5 61 93
36 96; fax: +33 5 61 93 45 80; email:
airworthiness.A330-A340@airbus.com;
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SUMMARY:
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internet: https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0169; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone:
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2018–0169; Product Identifier
2017–NM–095–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 2015–02–17,
Amendment 39–18084 (80 FR 4762,
January 29, 2015) (‘‘AD 2015–02–17’’),
for all Airbus Model A330–200, A330–
200 Freighter, and A330–300 series
airplanes. AD 2015–02–17 requires
revising the electrical emergency
configuration procedure in the
Emergency Procedures section of the
AFM to include procedures for
deploying the ram air turbine manually
to provide sufficient hydraulic power
and avoid CSM/G shedding. AD 2015–
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02–17 resulted from an electrical load
analysis that revealed that hydraulic
power might not be sufficient to supply
the CSM/G during slat/flap extension
when only one engine is running. We
issued AD 2015–02–17 to prevent CSM/
G shedding in conjunction with the loss
of the main electrical system, which
could lead to the scenario where the
flight crew is not clearly warned that the
electrical system has switched on the
battery and thus has a limited duration
that would allow a safe landing.
Actions Since AD 2015–02–17 Was
Issued
Since we issued AD 2015–02–17, we
have determined that replacement or
modification of the two FWCs is
necessary to address the identified
unsafe condition.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0105R1, dated July 17,
2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A330–200, A330–200 Freighter,
and A330–300 series airplanes. The
MCAI states:
The Constant Speed Motor/Generator
(CSM/G), as installed on Airbus A330
aeroplanes, is qualified for an overload
condition of 9.5 kVA [kilovolt-ampere] for 30
minutes. This duration is sufficient to
perform safe landing and go-around.
However, electrical load analysis revealed
that the hydraulic power might not be
sufficient to supply the CSM/G during slat/
flap extension, when only one engine is
running.
This condition, if not corrected, and in
conjunction with the loss of main system,
could lead to a scenario where the crew is
not clearly warned that the electrical system
has switched on the battery and thus has a
limited duration to support a safe landing.
To initially address this potential unsafe
condition, Airbus issued an Aircraft Flight
Manual (AFM) Temporary Revision (TR) to
amend the electrical emergency configuration
‘‘ELEC EMER CONFIG’’ procedure to require
the pilot to deploy the ram air turbine
manually before setting the Landing
Recovery to ‘‘ON’’ position, which provides
sufficient hydraulic power and avoids CSM/
G shedding under worst-case operational
conditions. Consequently, EASA issued AD
2014–0273 to require amendment of the AFM
by incorporating the applicable Airbus TR.
After finding that [EASA] AD 2014–0273
contained some incorrect and incomplete
information, EASA issued AD 2014–0281
[which corresponds to FAA AD 2015–02–17],
retaining the requirements of EASA AD
2014–0273, which was superseded, but
correcting the information related to premod/pre Service Bulletin (SB) or post-mod/
post SB aeroplane configurations.
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16249
Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
Since EASA AD 2014–0281 was issued, in
order to improve the ‘‘ELEC EMER CONFIG’’
procedure, Airbus developed modifications
to install improved Flight Warning Computer
(FWC), which is embodied in production
through Airbus modification (mod) 205228,
and to be embodied in service with Airbus
SB A330–31–3232 * * *.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0281, which is superseded, and
requires installation of a software standard
upgrade [or replacement] of the two FWCs
and removal of the applicable AFM TR once
the aeroplane is modified.
Since EASA AD 2017–0105 was issued, it
was identified that there was no need to
require removal of applicable AFM TR, nor
incorporation of a later AFM revision, as the
contents are identical. This revised [EASA]
AD deletes the requirement of paragraph (3)
[of EASA AD 2017–0105].
*
*
*
*
*
You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0169.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A330–31–3232, Revision 01, dated
February 14, 2017. The service
information describes procedures for
replacement or modification of the
FWCs. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Differences Between This Proposed AD
and the MCAI or Service Information
The MCAI applies to all Airbus Model
A330–200, A330–200 Freighter, and
A330–300 series airplanes. However,
this proposed AD excludes airplanes on
which Airbus modification 205228 has
been embodied in production.
Modification 205228 addresses the
unsafe condition specified in this
proposed AD. We have coordinated this
difference with EASA.
Costs of Compliance
We estimate that this proposed AD
affects 105 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Cost per
product
Labor cost
AFM revision (retained actions from AD
2015-02-17).
FWC modification or replacement (new proposed action).
1 work-hour × $85 per hour = $85 .................
$0
$85
$8,925
3 work-hours × $85 per hour = $255 .............
0
255
26,775
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
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Parts cost
Cost on U.S.
operators
Action
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Regulatory Findings
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
■
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Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
2015–02–17, Amendment 39–18084 (80
FR 4762, January 29, 2015), and adding
the following new AD:
Airbus: Docket No. FAA–2018–0169; Product
Identifier 2017–NM–095–AD.
(a) Comments Due Date
We must receive comments by May 31,
2018.
(b) Affected ADs
This AD replaces AD 2015–02–17,
Amendment 39–18084 (80 FR 4762, January
29, 2015) (‘‘AD 2015–02–17’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category, all
manufacturer serial numbers, except those
airplanes with Airbus modification 205228
embodied in production.
(1) Airbus Model A330–201, –202, –203,
–223, and –243 airplanes.
(2) Airbus Model A330–223F and –243F
airplanes.
(3) Airbus Model A330–301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 24, Electrical power.
(e) Reason
This AD was prompted by an electrical
load analysis that revealed that hydraulic
power might not be sufficient to supply the
constant speed motor/generator (CSM/G)
during slat/flap extension when only one
engine is running. We are issuing this AD to
prevent such a condition which, in
conjunction with the loss of the main
electrical system, could lead to the scenario
where the flight crew is not clearly warned
that the electrical system has switched on the
battery and thus has a limited duration that
would allow a safe landing.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Airplane Flight Manual (AFM)
Revision, With a New Exception
This paragraph restates the requirements of
paragraph (g) of AD 2015–02–17, with a new
exception. Except for airplanes identified in
paragraph (h) of this AD: Within 15 days after
February 13, 2015 (the effective date of AD
2015–02–17), revise the Emergency
Procedures section of the Airbus A330 AFM
to include the information in the applicable
Airbus temporary revision (TR) specified in
paragraph (g)(1) or (g)(2) of this AD. This may
be done by inserting a copy of the applicable
TR specified in paragraph (g)(1) or (g)(2) of
this AD into the AFM. Operate the airplane
according to the procedures in the applicable
TR. When the information in the applicable
TR has been included in the general revisions
of the AFM, the general revisions may be
inserted into the AFM, provided the relevant
information in the general revision is
identical to that in the TR, and the TR may
be removed.
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(1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067
configuration: Airbus A330/A340 AFM TR
TR427, UPDATE OF ELEC—EMER CONFIG
PROCEDURE, Issue 1.0, dated November 7,
2014.
(2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067
configuration: Airbus A330/A340 AFM TR
TR428, UPDATE OF ELEC—EMER CONFIG
PROCEDURE, Issue 1.0, dated November 7,
2014.
(h) New Airplanes Not Affected by the
Retained AFM Revision
Airplanes operated with an AFM that
incorporates the information in Airbus
EMERGENCY PROCEDURES/24ELECTRICAL POWER/ELEC—EMER
CONFIG Documentary Unit (DU)
00005218.0001001 (for airplanes in Airbus
pre-modification 47930 configuration and
pre-Airbus Service Bulletin A330–28–3067
configuration), or DU 00005218.0002001 (for
airplanes in an Airbus post-modification
47930 configuration or post-Airbus Service
Bulletin A330–28–3067 configuration), as
applicable, are compliant with the
requirements of paragraph (g) of this AD,
provided that the applicable DU is not
removed from the AFM.
(i) New Definitions
(1) For the purposes of this AD, an affected
FWC is a FWC standard lower than T7–0. An
FWC that is not affected is a FWC standard
T7–0 having part number (P/N)
LA2E20202T70000, or higher standard.
(2) For the purposes of this AD: Group 1
airplanes are those equipped with an affected
FWC (as defined in paragraph (i)(1) of this
AD) as of the effective date of this AD. Group
2 airplanes are those equipped with FWCs
that are not affected (as defined in paragraph
(i)(1) of this AD) as of the effective date of
this AD.
(j) New Requirement of This AD: FWC
Replacement or Modification
For Group 1 airplanes: Within 24 months
after the effective date of this AD: Replace or
modify an affected FWC with an FWC that
is not affected, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–31–3232, Revision 01,
dated February 14, 2017.
(k) Parts Installation Prohibition
(1) For Group 1 airplanes: After
accomplishing the actions required by
paragraph (j) of this AD, no person may
install an affected FWC on the modified
airplane.
(2) For Group 2 airplanes: As of the
effective date of this AD, no person may
install an affected FWC on any airplane.
(l) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (j) of this AD, if those
actions were performed before the effective
date of this AD using Airbus Service Bulletin
A330–31–3232, dated May 4, 2016.
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(m) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for AD
2015–02–17 are approved as an AMOC for
the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0105R1, dated July 17, 2017, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0169.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3229.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone: +33
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
airworthiness.A330-A340@airbus.com;
internet: https://www.airbus.com. You may
view this service information at the FAA,
Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information
on the availability of this material at the
FAA, call 206–231–3195.
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Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
Issued in Des Moines, Washington, on
March 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–06591 Filed 4–13–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0298; Product
Identifier 2017–NM–179–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318 and A319 series
airplanes; Model A320–211, A320–212,
A320–214, A320–216, A320–231, A320–
232, and A320–233 airplanes; and
Model A321–111, A321–112, A321–131,
A321–211, A321–212, A321–213, A321–
231, and A321–232 airplanes. This
proposed AD was prompted by reports
of missing assembly hardware on the
trimmable horizontal stabilizer actuator
(THSA). This proposed AD would
require repetitive inspections and
checks of the lower and upper THSA
attachments and applicable related
investigative and corrective actions; a
one-time inspection of the THSA lower
attachment and replacement as
applicable; and, for certain airplanes,
activation of the electrical load sensing
device (ELSD) and concurrent
modifications. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by May 31, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
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SUMMARY:
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16:32 Apr 13, 2018
Jkt 244001
p.m., Monday through Friday, except
Federal holidays.
For Airbus service information
identified in this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
internet https://www.airbus.com.
For United Technologies Corporation
Aerospace Systems (UTAS) service
information identified in this AD,
contact United Technologies
Corporation Aerospace Systems (UTAS):
Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England;
phone: +44 (0) 1902 624938; fax: +44 (0)
1902 788100; email:
techpubs.wolverhampton@
goodrich.com; internet: https://
www.goodrich.com/TechPubs.
You may view this service
information at the FAA, Transport
Standards Branch, 2200 South 216th
Street, Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0298; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198;
phone and fax: 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0298; Product Identifier 2017–
NM–179–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
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16251
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0237, dated December 4,
2017 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318 and A319 series airplanes;
Model A320–211, A320–212, A320–214,
A320–216, A320–231, A320–232, A320–
233 airplanes; and Model A321–111,
A321–112, A321–131, A321–211, A321–
212, A321–213, A321–231, and A321–
232 airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer
Actuator (THSA) of Airbus A320 Family
aeroplanes has been rig-tested to check
secondary load path behaviour in case of
primary load path failure. In that
configuration, the loads are transferred to the
secondary load path, which should jam,
preventing any Trimmable Horizontal
Stabilizer motion. The test results showed
that the secondary load path did not jam as
expected, preventing detection of the primary
load path failure. To verify the integrity of
the THSA primary load path and the correct
installation of the THSA, Airbus issued
Service Bulletin (SB) A320–27–1164, later
revised multiple times, and SB A320–
27A1179, and EASA issued AD 2006–0223
[which corresponds to FAA AD 2007–06–02,
Amendment 39–14983 (72 FR 12072, March
15, 2007) (‘‘AD 2007–06–02’’)], AD 2007–
0178 [which corresponds to FAA AD 2008–
09–16, Amendment 39–15497 (73 FR 24160,
May 2, 2008)(‘‘AD 2008–09–16’’)], AD 2008–
0150, and AD 2014–0147, each AD
superseding the previous one, requiring onetime and repetitive inspections.
Since EASA AD 2014–0147 was issued,
Airbus designed a new device, called
Electrical Load Sensing Device (ELSD), to
introduce a new mean of THSA upper
secondary load path engagement detection.
Consequently, Airbus issued several SBs
(Airbus SB A320–27–1245, A320–27–1246,
and A320–27–1247, depending on aeroplane
configuration) providing instructions to
install the wiring provision for ELSD
installation and to install ELSD on the THSA,
and SB A320–27–1248, providing
instructions to activate the ELSD. Airbus also
revised SB A320–27–1164, now at Revision
13, including instructions applicable for
aircraft equipped with ELSD.
Furthermore, following a visual inspection
of the THSA, an operator reported that the
THSA was found with a bush missing,
inducing torqueing of the THSA lower
attachment primary bolt against the THSA
lug, which resulted in the application of a
transverse force on the lug.
E:\FR\FM\16APP1.SGM
16APP1
]]>Agencies
[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)]
[Proposed Rules]
[Pages 16248-16251]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-06591]
[[Page 16248]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-02-
17, which applies to all Airbus Model A330-200, A330-200 Freighter, and
A330-300 series airplanes. AD 2015-02-17 requires revising the
electrical emergency configuration procedure in the Emergency
Procedures section of the airplane flight manual (AFM) to include
procedures for deploying the ram air turbine manually to provide
sufficient hydraulic power and avoid constant speed motor/generator
(CSM/G) shedding. Since we issued AD 2015-02-17, we have determined
that replacement or modification of the two flight warning computers
(FWCs) is necessary to address the identified unsafe condition. This
proposed AD would add a requirement to replace or modify the two FWCs.
This proposed AD would also remove airplanes from the applicability. We
are proposing this AD to address the unsafe condition on these
products.
DATES: We must receive comments on this proposed AD by May 31, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93
45 80; email: [email protected]; internet: https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0169; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Operations
office (telephone: 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0169;
Product Identifier 2017-NM-095-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued AD 2015-02-17, Amendment 39-18084 (80 FR 4762, January
29, 2015) (``AD 2015-02-17''), for all Airbus Model A330-200, A330-200
Freighter, and A330-300 series airplanes. AD 2015-02-17 requires
revising the electrical emergency configuration procedure in the
Emergency Procedures section of the AFM to include procedures for
deploying the ram air turbine manually to provide sufficient hydraulic
power and avoid CSM/G shedding. AD 2015-02-17 resulted from an
electrical load analysis that revealed that hydraulic power might not
be sufficient to supply the CSM/G during slat/flap extension when only
one engine is running. We issued AD 2015-02-17 to prevent CSM/G
shedding in conjunction with the loss of the main electrical system,
which could lead to the scenario where the flight crew is not clearly
warned that the electrical system has switched on the battery and thus
has a limited duration that would allow a safe landing.
Actions Since AD 2015-02-17 Was Issued
Since we issued AD 2015-02-17, we have determined that replacement
or modification of the two FWCs is necessary to address the identified
unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0105R1, dated July 17, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A330-200, A330-200 Freighter, and A330-300 series airplanes. The MCAI
states:
The Constant Speed Motor/Generator (CSM/G), as installed on
Airbus A330 aeroplanes, is qualified for an overload condition of
9.5 kVA [kilovolt-ampere] for 30 minutes. This duration is
sufficient to perform safe landing and go-around. However,
electrical load analysis revealed that the hydraulic power might not
be sufficient to supply the CSM/G during slat/flap extension, when
only one engine is running.
This condition, if not corrected, and in conjunction with the
loss of main system, could lead to a scenario where the crew is not
clearly warned that the electrical system has switched on the
battery and thus has a limited duration to support a safe landing.
To initially address this potential unsafe condition, Airbus
issued an Aircraft Flight Manual (AFM) Temporary Revision (TR) to
amend the electrical emergency configuration ``ELEC EMER CONFIG''
procedure to require the pilot to deploy the ram air turbine
manually before setting the Landing Recovery to ``ON'' position,
which provides sufficient hydraulic power and avoids CSM/G shedding
under worst-case operational conditions. Consequently, EASA issued
AD 2014-0273 to require amendment of the AFM by incorporating the
applicable Airbus TR.
After finding that [EASA] AD 2014-0273 contained some incorrect
and incomplete information, EASA issued AD 2014-0281 [which
corresponds to FAA AD 2015-02-17], retaining the requirements of
EASA AD 2014-0273, which was superseded, but correcting the
information related to pre-mod/pre Service Bulletin (SB) or post-
mod/post SB aeroplane configurations.
[[Page 16249]]
Since EASA AD 2014-0281 was issued, in order to improve the
``ELEC EMER CONFIG'' procedure, Airbus developed modifications to
install improved Flight Warning Computer (FWC), which is embodied in
production through Airbus modification (mod) 205228, and to be
embodied in service with Airbus SB A330-31-3232 * * *.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0281, which is superseded, and requires
installation of a software standard upgrade [or replacement] of the
two FWCs and removal of the applicable AFM TR once the aeroplane is
modified.
Since EASA AD 2017-0105 was issued, it was identified that there
was no need to require removal of applicable AFM TR, nor
incorporation of a later AFM revision, as the contents are
identical. This revised [EASA] AD deletes the requirement of
paragraph (3) [of EASA AD 2017-0105].
* * * * *
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0169.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A330-31-3232, Revision 01, dated
February 14, 2017. The service information describes procedures for
replacement or modification of the FWCs. This service information is
reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in
the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Differences Between This Proposed AD and the MCAI or Service
Information
The MCAI applies to all Airbus Model A330-200, A330-200 Freighter,
and A330-300 series airplanes. However, this proposed AD excludes
airplanes on which Airbus modification 205228 has been embodied in
production. Modification 205228 addresses the unsafe condition
specified in this proposed AD. We have coordinated this difference with
EASA.
Costs of Compliance
We estimate that this proposed AD affects 105 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
AFM revision (retained actions from AD 1 work-hour x $85 per $0 $85 $8,925
2015[dash]02[dash]17). hour = $85.
FWC modification or replacement (new 3 work-hours x $85 per 0 255 26,775
proposed action). hour = $255.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
[[Page 16250]]
2015-02-17, Amendment 39-18084 (80 FR 4762, January 29, 2015), and
adding the following new AD:
Airbus: Docket No. FAA-2018-0169; Product Identifier 2017-NM-095-AD.
(a) Comments Due Date
We must receive comments by May 31, 2018.
(b) Affected ADs
This AD replaces AD 2015-02-17, Amendment 39-18084 (80 FR 4762,
January 29, 2015) (``AD 2015-02-17'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers, except those airplanes with Airbus
modification 205228 embodied in production.
(1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Airbus Model A330-223F and -243F airplanes.
(3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 24, Electrical
power.
(e) Reason
This AD was prompted by an electrical load analysis that
revealed that hydraulic power might not be sufficient to supply the
constant speed motor/generator (CSM/G) during slat/flap extension
when only one engine is running. We are issuing this AD to prevent
such a condition which, in conjunction with the loss of the main
electrical system, could lead to the scenario where the flight crew
is not clearly warned that the electrical system has switched on the
battery and thus has a limited duration that would allow a safe
landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Airplane Flight Manual (AFM) Revision, With a New
Exception
This paragraph restates the requirements of paragraph (g) of AD
2015-02-17, with a new exception. Except for airplanes identified in
paragraph (h) of this AD: Within 15 days after February 13, 2015
(the effective date of AD 2015-02-17), revise the Emergency
Procedures section of the Airbus A330 AFM to include the information
in the applicable Airbus temporary revision (TR) specified in
paragraph (g)(1) or (g)(2) of this AD. This may be done by inserting
a copy of the applicable TR specified in paragraph (g)(1) or (g)(2)
of this AD into the AFM. Operate the airplane according to the
procedures in the applicable TR. When the information in the
applicable TR has been included in the general revisions of the AFM,
the general revisions may be inserted into the AFM, provided the
relevant information in the general revision is identical to that in
the TR, and the TR may be removed.
(1) For airplanes in Airbus pre-modification 47930 configuration
and pre-Airbus Service Bulletin A330-28-3067 configuration: Airbus
A330/A340 AFM TR TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue
1.0, dated November 7, 2014.
(2) For airplanes in Airbus post-modification 47930
configuration or post-Airbus Service Bulletin A330-28-3067
configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC--EMER
CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.
(h) New Airplanes Not Affected by the Retained AFM Revision
Airplanes operated with an AFM that incorporates the information
in Airbus EMERGENCY PROCEDURES/24-ELECTRICAL POWER/ELEC--EMER CONFIG
Documentary Unit (DU) 00005218.0001001 (for airplanes in Airbus pre-
modification 47930 configuration and pre-Airbus Service Bulletin
A330-28-3067 configuration), or DU 00005218.0002001 (for airplanes
in an Airbus post-modification 47930 configuration or post-Airbus
Service Bulletin A330-28-3067 configuration), as applicable, are
compliant with the requirements of paragraph (g) of this AD,
provided that the applicable DU is not removed from the AFM.
(i) New Definitions
(1) For the purposes of this AD, an affected FWC is a FWC
standard lower than T7-0. An FWC that is not affected is a FWC
standard T7-0 having part number (P/N) LA2E20202T70000, or higher
standard.
(2) For the purposes of this AD: Group 1 airplanes are those
equipped with an affected FWC (as defined in paragraph (i)(1) of
this AD) as of the effective date of this AD. Group 2 airplanes are
those equipped with FWCs that are not affected (as defined in
paragraph (i)(1) of this AD) as of the effective date of this AD.
(j) New Requirement of This AD: FWC Replacement or Modification
For Group 1 airplanes: Within 24 months after the effective date
of this AD: Replace or modify an affected FWC with an FWC that is
not affected, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-31-3232, Revision 01, dated February
14, 2017.
(k) Parts Installation Prohibition
(1) For Group 1 airplanes: After accomplishing the actions
required by paragraph (j) of this AD, no person may install an
affected FWC on the modified airplane.
(2) For Group 2 airplanes: As of the effective date of this AD,
no person may install an affected FWC on any airplane.
(l) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(j) of this AD, if those actions were performed before the effective
date of this AD using Airbus Service Bulletin A330-31-3232, dated
May 4, 2016.
(m) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (n)(2) of this AD. Information
may be emailed to: [email protected].
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 2015-02-17 are approved as
an AMOC for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0105R1, dated July 17, 2017, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0169.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3229.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: [email protected];
internet: https://www.airbus.com. You may view this service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195.
[[Page 16251]]
Issued in Des Moines, Washington, on March 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-06591 Filed 4-13-18; 8:45 am]
BILLING CODE 4910-13-P
